EP1731837A2 - Rotationally locked injection system for a turbine - Google Patents

Rotationally locked injection system for a turbine Download PDF

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Publication number
EP1731837A2
EP1731837A2 EP06076075A EP06076075A EP1731837A2 EP 1731837 A2 EP1731837 A2 EP 1731837A2 EP 06076075 A EP06076075 A EP 06076075A EP 06076075 A EP06076075 A EP 06076075A EP 1731837 A2 EP1731837 A2 EP 1731837A2
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EP
European Patent Office
Prior art keywords
injection system
cutout
sliding
sole
sliding bushing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06076075A
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German (de)
French (fr)
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EP1731837A3 (en
EP1731837B1 (en
Inventor
Daniel Bernier
Romain Lunel
Laurent Marnas
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1731837A2 publication Critical patent/EP1731837A2/en
Publication of EP1731837A3 publication Critical patent/EP1731837A3/en
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Publication of EP1731837B1 publication Critical patent/EP1731837B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a fuel injection system for a turbo-reactor. More specifically, it relates to an injection system which comprises a fixed part and a sliding bushing comprising a sole slidably mounted on a sliding surface of the fixed part of the injection system, the fixed part comprising anti-rotating means and the sole of the sliding bushing comprising complementary anti-rotating means which cooperate with those of the fixed part to limit the rotation of the sliding bushing relative to the fixed part.
  • the combustion chambers of the turbo-reactor comprise an inner wall and an outer wall connected at their upstream ends by an annular bottom to define an annular combustion chamber bottom.
  • Regularly distributed injection systems on the periphery of the bottom of the combustion chamber deliver a mixture of air and fuel which is ignited to provide combustion gases.
  • An injection system consists of a fixed part which includes one, and more generally two tendrils in which the air is rotated, a venturi and a bowl.
  • the fixed part also comprises a ring having a sliding surface.
  • a sliding bushing has a centering portion, generally a cone, for centering a fuel injector relative to the longitudinal axis of the tendril.
  • these anti-rotating means are constituted by a bowl having two parallel walls and a sole of the sliding bushing having two straight faces parallel to the sides of the sole.
  • a relatively large clearance is provided between the sole of the sliding bushing and the straight faces of the bowl in order to allow, as previously explained, to accommodate the differential expansions and manufacturing tolerances. Nevertheless, the clearance is sufficiently low to prevent complete rotation of the sliding bushing relative to the bowl of the injection system.
  • an anti-rotating device of this type is difficult to manufacture. It is therefore relatively expensive.
  • the present invention specifically relates to an injection system for a gas turbine engine, in particular for the propulsion of aircraft, which comprises simple anti-rotating means and therefore inexpensive to achieve.
  • the anti-rotating means of the sole are constituted by one or more cuts formed in the sole and in that the anti-rotating means of the fixed part are constituted by one or several lugs protruding into the cutout (s) of the sole of the sliding bushing.
  • the lug or lugs protrude from the sliding surface of the fixed part of the injection system.
  • the lug or lugs protrude from a closure ring which maintains the sliding passage on the fixed part of the injection system.
  • the cutout (s) can be opened or closed.
  • the sole of the sliding bushing comprises a first blank and a second blank, the first blank being relatively smaller than the second blank so that the first blank cuts alone. the rotation of the sliding bushing in a first operating step, the second cutting limiting the rotation of the sliding bushing after the wear of a lug protruding inside the cut.
  • FIG. 1 shows a partial schematic sectional view of a turbo-jet combustion chamber designated by the general reference 2 comprising an injection system according to the present invention.
  • the combustion chamber 2 has a form of longitudinal symmetry of revolution relative to a general axis of the turbine. It has an inner casing wall 4 and a outer casing wall 6.
  • An inner chamber wall 8 delimits a passage 10 with the inner casing wall 4 and an outer chamber wall 12 delimits a passage 14 with the outer casing wall 6.
  • each injection system 18 comprises a fixed part consisting of a ring 35 of a swirler 24, a venturi 25 and a bowl 28.
  • a sliding bushing 26 is slidably mounted on the ring 35
  • the swirler 24 is mounted on a bowl 28 having a flared shape connected to the chamber bottom 16 via a deflector 20 and a split ring 22.
  • the swirler 24 comprises a first blade stage 30, and a second blade stage 32 whose function is to drive the air in rotation around the longitudinal axis YY of the injection system.
  • the blades of the stages 30 and 32 may be in the same direction or in opposite directions.
  • a sliding surface 34 is provided on the ring 35.
  • the sliding bushing is slidably mounted on the sliding surface of the ring 35.
  • the bushing 26 comprises a sole 36 adapted to slide on the sliding surface of the ring. 34.
  • the sliding bushing further includes a centering portion, for example a centering cone 38 for centering a fuel injector 40 (FIG. 1) with respect to the injection system 18.
  • the sliding surface is extended externally by a peripheral rim 42 so as to form a shallow chamber in which the sole 36 is retained.
  • the chamber is closed by a cup 44 constituting a closure ring.
  • a relatively large clearance is provided between the periphery of the sole 36 of the sliding bushing 26 and the flange 42 located at the periphery of the ring 34.
  • This relatively large game is intended to accommodate the differential expansion differences that occur between the combustion chamber, raised to a high temperature and the fuel injector colder. On the other hand, it allows to accommodate manufacturing tolerances so that the injector 40 can be centered on the carburetor when the combustion chamber is mounted on the injectors.
  • the operation of the combustion chamber module is as follows.
  • the pressurized air from the compressor enters the combustion chamber through the passage 46, as shown by the arrow 48. Part of the air passes through the central opening of the fairing 50 as shown by the arrows 52, while that the remainder of the air flow is directed from outside the fairing 50 to the passages 10 and 14, as shown schematically by the arrows 54 and 56.
  • Openings 58 are provided in the inner and outer walls 8 and 12 of the chamber of combustion to allow the entry of air from the passages 10 and 14 as shown schematically by the arrows 60.
  • the air that enters the fairing 50 is rotated in the stages 30 and 32 of the auger and it mixes with the fuel delivered by the injector 40.
  • the gas mixture enters the combustion chamber in which it is ignited.
  • the injector system 18 comprises anti-rotating means to prevent the rotation of the sliding bushing relative to the fixed part of the injector system. Indeed, in the absence of such anti-rotating means, the sliding bushing, which must be able to move freely relative to the sliding surface 34, could rotate around the axis YY, especially under the effect of vibration, which would result in significant wear and, therefore, a significant reduction in the life of the injector and injector pin system.
  • the anti-rotating means are constituted by a cutout 62 formed in the soleplate 36 and a complementary lug 64 formed in the sliding surface 34 of the auger.
  • a relatively large clearance is provided between the lug 64 and the periphery of the cutout 62 so as not to prevent the displacement of the sliding bushing relative to the surface of the sliding 34, which allows the accommodation of the games and differential expansions as explained previously.
  • the sliding bushing can not move relative to the auger so that the lug 64 leaves the opening 62, so that the rotation of the sliding bushing is prevented.
  • the sliding bushing can pivot at a certain angle, which is a function of the clearance between the opening 62 and the lug, until the lug comes into abutment against the wall of the opening. After that, the rotation of the sliding bushing is blocked.
  • the lug (s) 64 may also be formed from the surface of the closure ring 44 which faces the sole 36 of the sliding bushing. Or again, in another embodiment, when the sole 36 has several cuts, some of the lugs may be formed from the sliding surface 34, while others are formed from the closure ring 44.
  • the parts which constitute the carburetor of the invention are made of very hard materials, for example of special steel, the most advantageous way of producing them is molding.
  • the lug 64 and the cutout 62 can be obtained directly from a foundry.
  • these parts can also be machined.
  • anti-rotating means preventing rotation of the sliding bushing by relative to the ring of the fixed part of the injection system.
  • the cut can have very varied shapes without departing from the scope of the invention.
  • the lug 64 may have a substantially rectangular shape and the cut 62 in the form of a sector having two flat walls 66 on which the lug 62 is supported.
  • the cutout can be opened, as in FIGS. 3 and 4. It can also be closed, as shown in FIG. 5.
  • the sole 36 has three circular perforations 62 constituting cutouts and three lugs 64, a penetrating spigot within each of the circular orifices 62.
  • Figure 6 shows yet another embodiment.
  • the sole 36 has a cut 62a and a cut 62b, the cut 62a being relatively smaller than the cut 62b.
  • the lug 64a located inside the cutout 62a which limits the rotation of the sliding bushing. Consequently, the lug 64b, located inside the cutout 62b, is not subject to any wear. If the lug 62a breaks due to wear, the lug 64b comes into operation which doubles the life of the anti-rotating means.
  • Fig. 7 shows a fourth embodiment.
  • the cutout 62 and the lug 64 have lateral edges whose extension passes through the axis of revolution 0 of the bowl and therefore by the axis of the injector (in operation).

Abstract

The system has a fixed part constituted of a ring (35) with a spin (24), and a sliding cross piece (26) with a base plate (36) slidingly mounted on a sliding surface of the fixed part. The plate has complementary anti-rotating units with a cut (62) formed in the plate, and the fixed part has anti-rotating units constituted by a pin (64) projecting from the cut to limit rotation of the cross piece with respect to the fixed part.

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention concerne un système d'injection de carburant pour turbo-réacteur. Plus précisément, elle concerne un système d'injection qui comprend une partie fixe et une traversée coulissante comportant une semelle montée coulissante sur une surface de glissement de la partie fixe du système d'injection, la partie fixe comportant des moyens anti-rotatifs et la semelle de la traversée coulissante comportant des moyens anti-rotatifs complémentaires qui coopèrent avec ceux de la partie fixe pour limiter la rotation de la traversée coulissante par rapport à la partie fixe.The invention relates to a fuel injection system for a turbo-reactor. More specifically, it relates to an injection system which comprises a fixed part and a sliding bushing comprising a sole slidably mounted on a sliding surface of the fixed part of the injection system, the fixed part comprising anti-rotating means and the sole of the sliding bushing comprising complementary anti-rotating means which cooperate with those of the fixed part to limit the rotation of the sliding bushing relative to the fixed part.

Les chambres de combustion des turbo-réacteur comprennent une paroi intérieure et une paroi extérieure reliées à leurs extrémités amont par un fond annulaire pour définir un fond de chambre de combustion annulaire. Des systèmes d'injection régulièrement répartis sur la périphérie du fond de la chambre de combustion délivrent un mélange d'air et de carburant qui est enflammé pour fournir des gaz de combustion.The combustion chambers of the turbo-reactor comprise an inner wall and an outer wall connected at their upstream ends by an annular bottom to define an annular combustion chamber bottom. Regularly distributed injection systems on the periphery of the bottom of the combustion chamber deliver a mixture of air and fuel which is ignited to provide combustion gases.

Un système d'injection est constitué d'une partie fixe qui comprend une, et plus généralement deux vrilles dans lesquelles l'air est entraîné en rotation, un venturi et un bol. La partie fixe comprend également une bague comportant une surface de glissement. Une traversée coulissante comporte une partie de centrage, généralement un cône, est destinée à centrer un injecteur de carburant par rapport à l'axe longitudinal de la vrille.An injection system consists of a fixed part which includes one, and more generally two tendrils in which the air is rotated, a venturi and a bowl. The fixed part also comprises a ring having a sliding surface. A sliding bushing has a centering portion, generally a cone, for centering a fuel injector relative to the longitudinal axis of the tendril.

Il est connu dans l'état de la technique, de monter la traversée coulissante, coulissante par rapport à la partie fixe du système d'injection afin, d'une part, d'accommoder les déplacements relatifs de la chambre et de l'injecteur de carburant par suite des dilatations différentielles des différentes parties constitutives du moteur et, d'autre part, pour tenir compte des tolérances de fabrication. Le brevet US 5,117,624 décrit une traversée coulissante de ce type. Par ailleurs, il est nécessaire de prévoir des moyens anti-rotatifs afin d'empêcher une rotation de la traversée coulissante par rapport à la partie fixe du système d'injection. En effet, cette rotation, lorsqu'elle peut se produire, entraîne une usure rapide des pièces et réduit de manière importante leur durée de fonctionnement. Dans le dispositif décrit dans le brevet américain cité plus haut, ces moyens anti-rotatifs sont constitués par une cuvette présentant deux parois parallèles et par une semelle de la traversée coulissante comportant deux faces droites parallèles aux côtés de la semelle. Un jeu relativement important est prévu entre la semelle de la traversée coulissante et les faces droites de la cuvette afin de permettre, comme on l'a exposé précédemment, d'accommoder les dilatations différentielles et les tolérances de fabrication. Néanmoins, le jeu est suffisamment faible pour empêcher une rotation complète de la traversée coulissante par rapport à la cuvette du système d'injection. Toutefois, un dispositif anti-rotatif de ce type est difficile à fabriquer. Il est donc relativement coûteux.It is known in the state of the art, to mount the sliding bushing, sliding relative to the fixed part of the injection system, on the one hand, to accommodate the relative movements of the chamber and the injector of fuel as a result of the differential expansions of the various constituent parts of the engine and, on the other hand, to take account of manufacturing tolerances. The patent US 5,117,624 describes a sliding traverse of this type. Furthermore, it is necessary to provide anti-rotating means to prevent rotation of the sliding bushing relative to the fixed part of the injection system. Indeed, this rotation, when it can occur, causes rapid wear of the parts and significantly reduces their operating time. In the device described in the US patent cited above, these anti-rotating means are constituted by a bowl having two parallel walls and a sole of the sliding bushing having two straight faces parallel to the sides of the sole. A relatively large clearance is provided between the sole of the sliding bushing and the straight faces of the bowl in order to allow, as previously explained, to accommodate the differential expansions and manufacturing tolerances. Nevertheless, the clearance is sufficiently low to prevent complete rotation of the sliding bushing relative to the bowl of the injection system. However, an anti-rotating device of this type is difficult to manufacture. It is therefore relatively expensive.

La présente invention a précisément pour objet un système d'injection pour un moteur à turbine à gaz, en particulier pour la propulsion d'avions, qui comporte des moyens anti-rotatifs simples et donc peu coûteux à réaliser.The present invention specifically relates to an injection system for a gas turbine engine, in particular for the propulsion of aircraft, which comprises simple anti-rotating means and therefore inexpensive to achieve.

Ces buts sont atteints conformément à l'invention par le fait que les moyens anti-rotatifs de la semelle sont constitués par une ou plusieurs découpes formées dans la semelle et en ce que les moyens anti-rotatifs de la partie fixe sont constitués par un ou plusieurs ergots faisant saillie dans la ou les découpes de la semelle de la traversée coulissante.These objects are achieved according to the invention in that the anti-rotating means of the sole are constituted by one or more cuts formed in the sole and in that the anti-rotating means of the fixed part are constituted by one or several lugs protruding into the cutout (s) of the sole of the sliding bushing.

Une telle solution est simple à réaliser. De plus, la découpe procure une diminution du poids de la traversée coulissante.Such a solution is simple to achieve. In addition, cutting provides a reduction in the weight of the sliding bushing.

Dans une réalisation particulière, le ou les ergots font saillie à partir de la surface de glissement de la partie fixe du système d'injection.In a particular embodiment, the lug or lugs protrude from the sliding surface of the fixed part of the injection system.

Dans une autre réalisation, le ou les ergots font saillie à partir d'une bague de fermeture qui maintient la traversée coulissante sur la partie fixe du système d'injection.In another embodiment, the lug or lugs protrude from a closure ring which maintains the sliding passage on the fixed part of the injection system.

La ou les découpes peuvent être ouvertes ou fermées.The cutout (s) can be opened or closed.

Dans une autre réalisation encore, la semelle de la traversée coulissante comporte une première découpe et une seconde découpe, la première découpe étant relativement plus petite que la seconde découpe de manière que la première découpe limite seule la rotation de la traversée coulissante dans une première étape de fonctionnement, la seconde découpe limitant la rotation de la traversée coulissante après l'usure d'un ergot faisant saillie à l'intérieur de la découpe.In yet another embodiment, the sole of the sliding bushing comprises a first blank and a second blank, the first blank being relatively smaller than the second blank so that the first blank cuts alone. the rotation of the sliding bushing in a first operating step, the second cutting limiting the rotation of the sliding bushing after the wear of a lug protruding inside the cut.

D'autres caractéristiques et avantages de l'invention apparaîtront encore à la lecture de la description qui suit d'exemples de réalisation donnés à titre illustratif en référence aux figures annexées. Sur ces figures :

  • la figure 1 est une vue générale en coupe d'une chambre de combustion de turbo-réacteur comportant un système d'injection conforme à la présente invention ;
  • la figure 2 est une vue en coupe à échelle agrandie du système d'injection de la figure 1 ;
  • la figure 3 est une vue en perspective de ce même système d'injection ;
  • les figures 4 à 7 représentent quatre variantes de réalisation différentes des moyens anti-rotatifs d'un système d'injection conforme à l'invention.
Other features and advantages of the invention will become apparent on reading the following description of exemplary embodiments given by way of illustration with reference to the appended figures. In these figures:
  • Figure 1 is a general sectional view of a turbo-jet combustion chamber comprising an injection system according to the present invention;
  • Figure 2 is an enlarged sectional view of the injection system of Figure 1;
  • Figure 3 is a perspective view of the same injection system;
  • Figures 4 to 7 show four different embodiments of the anti-rotating means of an injection system according to the invention.

On a représenté sur la figure 1 une vue schématique partielle, en coupe d'une chambre de combustion de turbo-réacteur désignée par la référence générale 2 comportant un système d'injection conforme à la présente invention. La chambre de combustion 2 présente une forme de symétrie longitudinale de révolution par rapport à un axe général de la turbine. Elle comporte une paroi de carter intérieure 4 et une paroi de carter extérieure 6. Une paroi de chambre intérieure 8 délimite un passage 10 avec la paroi de carter intérieure 4 et une paroi de chambre extérieure 12 délimite un passage 14 avec la paroi de carter extérieure 6.FIG. 1 shows a partial schematic sectional view of a turbo-jet combustion chamber designated by the general reference 2 comprising an injection system according to the present invention. The combustion chamber 2 has a form of longitudinal symmetry of revolution relative to a general axis of the turbine. It has an inner casing wall 4 and a outer casing wall 6. An inner chamber wall 8 delimits a passage 10 with the inner casing wall 4 and an outer chamber wall 12 delimits a passage 14 with the outer casing wall 6.

Les parois de chambre intérieure 8 et extérieure 12 sont réunies par un fond de chambre 16 à leurs extrémités amont. Une pluralité de système d'injection, typiquement quatorze à vingt-deux, régulièrement espacés angulairement (un seul système d'injection a été représenté sur la figure 1) sont prévus sur le fond de chambre 16. Comme on peut le voir plus en détail sur la figure 2, chaque système d'injection 18 comprend une partie fixe constituée d'une bague 35 d'une vrille 24, d'un venturi 25 et d'un bol 28. Une traversée coulissante 26 est montée coulissante sur la bague 35. La vrille 24 est montée sur un bol 28 présentant une forme évasée raccordée au fond de chambre 16 par l'intermédiaire d'un déflecteur 20 et d'une bague fendue 22. La vrille 24 comporte un premier étage d'aubes 30, et un deuxième étage d'aubes 32 qui ont pour fonction d'entraîner l'air en rotation autour de l'axe longitudinal Y-Y du système d'injection. Les aubes des étages 30 et 32 peuvent être de même sens ou de sens contraire. Une surface de glissement 34 est prévue sur la bague 35. La traversée coulissante est montée glissante sur la surface de glissement de la bague 35. A cet effet, la traversée 26 comporte une semelle 36 apte à glisser sur la surface de glissement de la bague 34. La traversée coulissante comporte en outre une partie de centrage, par exemple un cône de centrage 38, destinée à centrer un injecteur de carburant 40 (figure 1) par rapport au système d'injection 18.The inner chamber 8 and outer 12 walls are joined by a chamber bottom 16 at their upstream ends. A plurality of injection systems, typically fourteen to twenty-two, regularly spaced angularly (only one injection system has been shown in Figure 1) are provided on the chamber floor 16. As can be seen in more detail in FIG. 2, each injection system 18 comprises a fixed part consisting of a ring 35 of a swirler 24, a venturi 25 and a bowl 28. A sliding bushing 26 is slidably mounted on the ring 35 The swirler 24 is mounted on a bowl 28 having a flared shape connected to the chamber bottom 16 via a deflector 20 and a split ring 22. The swirler 24 comprises a first blade stage 30, and a second blade stage 32 whose function is to drive the air in rotation around the longitudinal axis YY of the injection system. The blades of the stages 30 and 32 may be in the same direction or in opposite directions. A sliding surface 34 is provided on the ring 35. The sliding bushing is slidably mounted on the sliding surface of the ring 35. For this purpose, the bushing 26 comprises a sole 36 adapted to slide on the sliding surface of the ring. 34. The sliding bushing further includes a centering portion, for example a centering cone 38 for centering a fuel injector 40 (FIG. 1) with respect to the injection system 18.

La surface de glissement est prolongée extérieurement par un rebord périphérique 42 de manière à former une chambre peu profonde dans laquelle la semelle 36 est retenue. La chambre est fermée par une coupelle 44 constituant une bague de fermeture.The sliding surface is extended externally by a peripheral rim 42 so as to form a shallow chamber in which the sole 36 is retained. The chamber is closed by a cup 44 constituting a closure ring.

Un jeu relativement important est prévu entre la périphérie de la semelle 36 de la traversée coulissante 26 et le rebord 42 situé à la périphérie de la bague 34. Ce jeu relativement important a pour but d'accommoder les différences de dilatation différentielle qui se produisent entre la chambre de combustion, portée à une température élevée et l'injecteur de carburant plus froid. D'autre part, il permet d'accommoder les tolérances de fabrication de manière que l'injecteur 40 puisse se centrer sur le carburateur lorsque l'on monte la chambre de combustion sur les injecteurs.A relatively large clearance is provided between the periphery of the sole 36 of the sliding bushing 26 and the flange 42 located at the periphery of the ring 34. This relatively large game is intended to accommodate the differential expansion differences that occur between the combustion chamber, raised to a high temperature and the fuel injector colder. On the other hand, it allows to accommodate manufacturing tolerances so that the injector 40 can be centered on the carburetor when the combustion chamber is mounted on the injectors.

Le fonctionnement du module chambre de combustion est le suivant. L'air sous pression en provenance du compresseur pénètre dans la chambre de combustion par le passage 46, comme schématisé par la flèche 48. Une partie de l'air passe dans l'ouverture centrale du carénage 50 comme schématisé par les flèches 52, tandis que le reste du flux d'air est dirigé par l'extérieur du carénage 50 vers les passages 10 et 14, comme schématisé par les flèches 54 et 56. Des ouvertures 58 sont prévues dans les parois intérieure et extérieure 8 et 12 de la chambre de combustion afin de permettre l'entrée de l'air à partir des passages 10 et 14 comme schématisé par les flèches 60.The operation of the combustion chamber module is as follows. The pressurized air from the compressor enters the combustion chamber through the passage 46, as shown by the arrow 48. Part of the air passes through the central opening of the fairing 50 as shown by the arrows 52, while that the remainder of the air flow is directed from outside the fairing 50 to the passages 10 and 14, as shown schematically by the arrows 54 and 56. Openings 58 are provided in the inner and outer walls 8 and 12 of the chamber of combustion to allow the entry of air from the passages 10 and 14 as shown schematically by the arrows 60.

L'air qui pénètre dans le carénage 50 est mis en rotation dans les étages 30 et 32 de la vrille et il se mélange au carburant délivré par l'injecteur 40. Le mélange gazeux pénètre dans la chambre de combustion dans laquelle il est enflammé.The air that enters the fairing 50 is rotated in the stages 30 and 32 of the auger and it mixes with the fuel delivered by the injector 40. The gas mixture enters the combustion chamber in which it is ignited.

De manière connue, le système injecteur 18 comporte des moyens anti-rotatifs pour empêcher la rotation de la traversée coulissante par rapport à la partie fixe du système injecteur. En effet, en l'absence de tels moyens anti-rotatifs, la traversée coulissante, qui doit pouvoir se déplacer librement par rapport à la surface de glissement 34, pourrait tourner autour de l'axe Y-Y, notamment sous l'effet des vibrations, ce qui se traduirait par une usure importante et, par conséquent, par une réduction importante de la durée de vie du système d'injecteur et d'axe d'injecteur.In known manner, the injector system 18 comprises anti-rotating means to prevent the rotation of the sliding bushing relative to the fixed part of the injector system. Indeed, in the absence of such anti-rotating means, the sliding bushing, which must be able to move freely relative to the sliding surface 34, could rotate around the axis YY, especially under the effect of vibration, which would result in significant wear and, therefore, a significant reduction in the life of the injector and injector pin system.

Comme on peut le voir sur la figure 3 qui représente une vue en perspective du système d'injection 18 de l'invention, la bague de fermeture 44 ayant été ôtée, les moyens anti-rotatifs sont constitués par une découpe 62 formée dans la semelle 36 et par un ergot complémentaire 64 formé dans la surface de glissement 34 de la vrille. Comme on le remarque en outre sur la figure 3, un jeu relativement important est prévu entre l'ergot 64 et la périphérie de la découpe 62 de manière à ne pas empêcher le déplacement de la traversée coulissante par rapport à la surface de glissement 34, ce qui permet l'accommodation des jeux et des dilatations différentielles comme on l'a expliqué antérieurement. Toutefois, la traversée coulissante ne peut pas se déplacer par rapport à la vrille de manière telle que l'ergot 64 sorte de l'ouverture 62, de telle sorte que la rotation de la traversée coulissante est empêchée. La traversée coulissante peut pivoter d'un certain angle, qui est fonction du jeu entre l'ouverture 62 et l'ergot, jusqu'à ce que l'ergot vienne en butée contre la paroi de l'ouverture. Après cela, la rotation de la traversée coulissante est bloquée.As can be seen in Figure 3 which shows a perspective view of the injection system 18 of the invention, the closure ring 44 having been removed, the anti-rotating means are constituted by a cutout 62 formed in the soleplate 36 and a complementary lug 64 formed in the sliding surface 34 of the auger. As is also noted in Figure 3, a relatively large clearance is provided between the lug 64 and the periphery of the cutout 62 so as not to prevent the displacement of the sliding bushing relative to the surface of the sliding 34, which allows the accommodation of the games and differential expansions as explained previously. However, the sliding bushing can not move relative to the auger so that the lug 64 leaves the opening 62, so that the rotation of the sliding bushing is prevented. The sliding bushing can pivot at a certain angle, which is a function of the clearance between the opening 62 and the lug, until the lug comes into abutment against the wall of the opening. After that, the rotation of the sliding bushing is blocked.

En variante de réalisation, le ou les ergots 64 peuvent également être formés à partir de la surface de la bague de fermeture 44 qui fait face à la semelle 36 de la traversée coulissante. Ou bien encore, dans une autre variante de réalisation, lorsque la semelle 36 comporte plusieurs découpes, certains des ergots peuvent être formés à partir de la surface de glissement 34, tandis que d'autres sont formés à partir de la bague de fermeture 44.As an alternative embodiment, the lug (s) 64 may also be formed from the surface of the closure ring 44 which faces the sole 36 of the sliding bushing. Or again, in another embodiment, when the sole 36 has several cuts, some of the lugs may be formed from the sliding surface 34, while others are formed from the closure ring 44.

Etant donné que les pièces qui constituent le carburateur de l'invention sont réalisées en des matériaux très durs, par exemple en acier spécial, la manière la plus avantageuse de les réaliser est le moulage. Ainsi, l'ergot 64 et la découpe 62 peuvent être obtenus directement de fonderie. Toutefois, dans une variante de réalisation, ces parties peuvent également être usinées. On réalise ainsi, de manière simple et peu coûteuse des moyens anti-rotatifs empêchant la rotation de la traversée coulissante par rapport à la bague de la partie fixe du système d'injection.Since the parts which constitute the carburetor of the invention are made of very hard materials, for example of special steel, the most advantageous way of producing them is molding. Thus, the lug 64 and the cutout 62 can be obtained directly from a foundry. However, in an alternative embodiment, these parts can also be machined. Thus, in a simple and inexpensive manner, anti-rotating means preventing rotation of the sliding bushing by relative to the ring of the fixed part of the injection system.

La découpe peut présenter des formes très variées sans sortir du cadre de l'invention. Ainsi, comme représenté sur la figure 4, l'ergot 64 peut présenter une forme sensiblement rectangulaire et la découpe 62 la forme d'un secteur comportant deux parois planes 66 sur lesquelles l'ergot 62 vient prendre appui.The cut can have very varied shapes without departing from the scope of the invention. Thus, as shown in Figure 4, the lug 64 may have a substantially rectangular shape and the cut 62 in the form of a sector having two flat walls 66 on which the lug 62 is supported.

La découpe peut être ouverte, comme sur les figures 3 et 4. Elle peut également être fermée, comme représenté sur la figure 5. Dans ce mode de réalisation, la semelle 36 comporte trois perforations circulaires 62 constituant des découpes et trois ergots 64, un ergot pénétrant à l'intérieur de chacun des orifices circulaires 62.The cutout can be opened, as in FIGS. 3 and 4. It can also be closed, as shown in FIG. 5. In this embodiment, the sole 36 has three circular perforations 62 constituting cutouts and three lugs 64, a penetrating spigot within each of the circular orifices 62.

La figure 6 représente encore un autre mode de réalisation. La semelle 36 comporte une découpe 62a et une découpe 62b, la découpe 62a étant relativement plus petite que la découpe 62b. De la sorte, c'est l'ergot 64a, situé à l'intérieur de la découpe 62a qui limite la rotation de la traversée coulissante. En conséquence, l'ergot 64b, situé à l'intérieur de la découpe 62b, n'est sujet à aucune usure. Si l'ergot 62a vient à se rompre par suite d'usure, l'ergot 64b entre en fonction ce qui double la durée de vie des moyens anti-rotatifs.Figure 6 shows yet another embodiment. The sole 36 has a cut 62a and a cut 62b, the cut 62a being relatively smaller than the cut 62b. In this way, it is the lug 64a, located inside the cutout 62a which limits the rotation of the sliding bushing. Consequently, the lug 64b, located inside the cutout 62b, is not subject to any wear. If the lug 62a breaks due to wear, the lug 64b comes into operation which doubles the life of the anti-rotating means.

La figure 7 représente un quatrième mode de réalisation. La découpe 62 et l'ergot 64 possèdent des bords latéraux dont le prolongement passe par l'axe de révolution 0 du bol et donc par l'axe de l'injecteur (en fonctionnement).Fig. 7 shows a fourth embodiment. The cutout 62 and the lug 64 have lateral edges whose extension passes through the axis of revolution 0 of the bowl and therefore by the axis of the injector (in operation).

Claims (6)

Système d'injection de carburant pour turbo-réacteur comportant une partie fixe (24) et une traversée coulissante (26) comportant une semelle (36) montée coulissante sur une surface de glissement de la partie fixe, la partie fixe (24) comportant des moyens anti-rotatifs et la semelle de la traversée coulissante (26) comportant des moyens anti-rotatifs complémentaires qui coopèrent avec les moyens anti-rotatifs de la traversée coulissante pour limiter la rotation de la traversée coulissante par rapport à la partie fixe, caractérisé en ce que les moyens anti-rotatifs de la semelle coulissante sont constitués par au moins une découpe (62) formée dans la semelle (36) et en ce que les moyens anti-rotatifs de la partie fixe sont constitués par au moins un ergot (64) faisant saillie dans ladite au moins une découpe (62) de la semelle de la traversée coulissante.A turbo-jet fuel injection system comprising a fixed portion (24) and a sliding bushing (26) having a sole (36) slidably mounted on a sliding surface of the fixed portion, the fixed portion (24) having anti-rotating means and the sole of the sliding bushing (26) having complementary anti-rotating means which cooperate with the anti-rotating means of the sliding bushing to limit the rotation of the sliding bushing relative to the fixed part, characterized in that that the anti-rotating means of the sliding sole are constituted by at least one cutout (62) formed in the sole (36) and in that the means anti-rotating of the fixed part are constituted by at least one lug (64 ) protruding into said at least one cutout (62) of the sole of the sliding bushing. Système d'injection selon la revendication 1, caractérisé en ce qu'un ou des ergots (64) font saillie à partir de la surface de glissement (34) de la partie fixe.Injection system according to claim 1, characterized in that one or more lugs (64) project from the sliding surface (34) of the fixed part. Système d'injection selon la revendication 1 ou 2, caractérisé en ce qu'un ou des ergots (64) font saillie à partir d'une bague de retenue (44) qui maintient la traversée coulissante (26) sur la partie fixe.Injection system according to claim 1 or 2, characterized in that one or more lugs (64) project from a retaining ring (44) which holds the sliding bushing (26) on the fixed part. Système d'injection selon l'une des revendications 1 à 3, caractérisé en ce que la ou les découpes (62) sont ouvertes.Injection system according to one of claims 1 to 3, characterized in that the cutout (s) (62) are open. Système d'injection selon l'une des revendications 1 à 3, caractérisé en ce que la ou les découpes (62) sont fermées.Injection system according to one of claims 1 to 3, characterized in that the cutout (s) (62) are closed. Système d'injection selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la semelle (36) de la traversée coulissante comporte une première découpe (62a) et une seconde découpe (62b), la première découpe (62a) étant relativement plus petite que la seconde découpe (62b) de manière que la première découpe (62a) et un ergot (64a) faisant saillie à l'intérieur de cette découpe limitent seul la rotation de la traversée coulissante dans une première étape de fonctionnement, la seconde découpe (62b) limitant la rotation de la traversée coulissante après l'usure de l'ergot (64a) faisant saillie à l'intérieur de la découpe (62a).Injection system according to any one of claims 1 to 5, characterized in that the sole (36) of the sliding bushing comprises a first cutout (62a) and a second cutout (62b), the first cutout (62a) being relatively smaller than the second cutout (62b) so that the first cutout (62a) and a projection (64a) projecting therein limit only the rotation of the slideway in a first operating step, the second cut (62b) limiting the rotation of the sliding bushing after the wear of the lug (64a) projecting inside the cutout (62a).
EP06076075.8A 2005-06-07 2006-05-19 Rotationally locked injection system for a turbine Active EP1731837B1 (en)

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FR0551518A FR2886714B1 (en) 2005-06-07 2005-06-07 ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR

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EP1731837A3 EP1731837A3 (en) 2013-05-01
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EP (1) EP1731837B1 (en)
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FR3040765A1 (en) * 2015-09-09 2017-03-10 Snecma SUPPORTING ELEMENT FOR DAMPING AXIAL MOVEMENTS OF SLIDING INJECTION SYSTEM FOR TURBOMACHINE
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Also Published As

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RU2416054C2 (en) 2011-04-10
CN1891999B (en) 2010-10-06
FR2886714B1 (en) 2007-09-07
FR2886715B1 (en) 2007-08-31
US7591136B2 (en) 2009-09-22
US20070033950A1 (en) 2007-02-15
FR2886714A1 (en) 2006-12-08
EP1731837A3 (en) 2013-05-01
CA2551498C (en) 2014-03-18
EP1731837B1 (en) 2014-10-08
CN1891999A (en) 2007-01-10
CA2551498A1 (en) 2007-01-06
FR2886715A1 (en) 2006-12-08
RU2006119424A (en) 2007-12-20

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